Stabilizer for flying-machines.



Pafented Dec. 3, 1918.

2 SHEETS-SHEET I.

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Fnarziz W/zL'Z-e *Wam was F. WHITE.

STABILIZER FOR FLYING MACHINES.

APPLICATION FILED SEPT. 22, m 1.

Patented Dec. 3, 1918.

2 SHEETS-SHEET 2.

avwamtoz lvaw Fnaazk Mia/ta v Whey ream; wmrs, or SUMMITVILLE, NEW YORK STABXLliZER FtJR FLYING-MA CHINES.

Application filed September 22, 1917. Serial No. 192,725.

To all lclmmv it may concern:

to it known that I, FRANK \Vnrm, a sub jcct oi the Emperor of Germany, residing at Sunnuitville, in the county of Sullivan and State of New York; have invented new and useful lmproven'ients in Stabilizers for Flyiugfllachinea, of which the following is a. spw-ilicatiou.

This invention relates to stal'iilizingn'ieans for aircraft, the same hcing; especially designed with reference to the needs of an airplane. Y

'lhe ohjcct oi the invention is to provide a simple appliance capahle oi lieing applied to and used inconjuin'tion with any type of airplane, for the purpose of automatically controlling the balancing surfaces of a inachine. thcrchr relieving the aviator to that extent. p

A further object oi the invention is to provide stabilizing means of the character ahore referred to which may beconlrolleil hy the operator when he desires'to adjust. the angle of ascent or descent as in rising" from the L'round preparatory to actual flight and in hulking: a landing at ihecnd of a flight.

"With the ahore and other ohjects in \'ic\\. lhc im'cnl ion consists in the norcl cou slrucliou. conihination and arrangement oi parts. herein fully dcscrihod. illustrated and claimed.

in the :u-com panyiin: drawiugs:--

Figure l is a pcrspcciiw diagram of an airplane. showing the improved stabilizer in its applied relatii'm thereto.

stabilizer.

Fig. 3 is a side elevation of an airplane illustrating the applied relation ol the still)- ilizer thereto.

Fig, 4 is an enlarged fore and aft vertical longitudinal section throng the stabilizer.

The stahilizer in the preferred emhodiment thereof comprises aholloiv spherical body designated generally at A and shown as comprising a hottoin section 1 and a top section 2, the hottom section I heing of greater extent and capacity than the top section 2 and the top or cover section 2 lieing secured hy a liquid tight joint'lo the hot-' tom section It hy any suitable fastening means 3.

The body it adapted to contain water or other liquid indicated at 4' and is suspended by means of upwardly extending Specification of Letters Patent.

Fig.1. 2 is an enlarged sectional view of tho Patentod Dec. 3,1918.

arms 5- from hangers 0 extending downwardly from a part 7 of an airplane, such as one of the supporting surfaces or planes.

sal joint: 10. is a disk 11 of any suitable description. (,onnected to the disk 11 is a plurality oi' upwardly exl'e'mling-rods l2 and 13. The rods 12 are arranged at opposite sides at the hanger or shaft 9 whilethe rods i i are arranged one in advance and one in rear of the hanger or shaft 9. The rods ii are connected to thecontrols 14 which actuate the lateral balancing surfaces. while the rods 13 are connected to the controls 15 which operate the horizontal rudder.

From the foregoing description taken in connection with the accompanying drawings it will now he understood that when the airplane. dips to the right or to the left or when the front of, the machine inclines dowm ardly or upwardly. the water-or other liquid 4 in thehod A will shift'its position and cause a corresponding angular disposiiion oi the disk 11 which lies in contact at all times wiihthewaicr immediately adja- 90 cent to the surface thereof. As a result of the movement. of the disk 11. one or more of the rods 12 and 13 will he moved upwardly while the other rod or rods will be moved downwardly. The controls which connect said rods with the fore and aft and lateral balancmgplanes or surfaces will be correspondingly pulled or slackcd with the result that the equilibrium of the airplane will be automatically restored. No attention what- 106 ever is required on the part of the aviator 7 who mav therefore direct his entire attem iion to the other controls and even make the :uljust'ments oiihe engine and the equipment; thereof.

I do not: desire to he limitedio the exact construction illustrated and descrihedas it will he apparent that the number of rods 12 and iii may he increased or diminished according to the nluulu'ufloi' devices to he 0051- W trolled ihcrclrv. 'lhcse and other changes in the form, proportion and minor details of construction may be resorted to without de- -parting fromthe principl or sacrificing any of the advantages of the'invention.

While the stabilizer has been described as useful in. connection with flying machines and aircraft in general, it will be apparent that said stabilizer may also be used with equal eflicieney in conjunction with subma rine vessels.

I claim 1. Stabilizing means for aircraft, comprising a liquid containing bodyya member hers in front and in rear of the center 0]: the body converging upwardly to a meeting point in line with the rertical axis of the body.

2. Stabilizing means for aircraft coinprising a liquid containing body, a member mounted for movement therein controlled by the shitting of the liquid, and a plurality of controlling members arranged to be actualed by said liquid controlled member for automatically shifting the controlling surlaces of an airplane, said liquid controlled member being hung on a universal joint so as to swing under the influence of the liquid in any direction.

In. testimony whereof I aHiX my signature.

FRANK WHITE. 

